BUDGE BUDGE INSTITUTE OF TECHNOLOGYMECHANICAL ENGINEERING

STEAM NOZZLE APROJECT ON

Presented By

ROHAN ROY

What is a steam nozzle????

A nozzle is a device designed to control the direction or characteristics of a fluid flow (especially to increase velocity) as it exits (or enters) an enclosed chamber or pipe.A nozzle is often a pipe or tube of varying cross sectional area, and it can be used to direct or modify the flow of a fluid (liquid or gas). Nozzles are frequently used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that emerges from them.Finally the goal of a nozzle is to increase the kinetic energy of the flowing medium at the expense of its pressure and internal energy.

INTRODUCTION

Convergent:- The cross section of nozzle tapers to a smaller section allow for changes which occur due changes in velocity, specific volume dryness fraction – as the flow expands, it has lower expansion ratio and hence lower outlet velocities.

Convergent-----Divergent:- The nozzle which converges to throat and diverges afterwards. It has higher expansion ratio – as addition of divergent portion produces steam of higher velocities.Eg- De-Laval Nozzle

Divergent:- A nozzle whose cross section becomes larger in the direction of flow is known as divergent nozzle.

Types of nozzlesThree types of nozzles:-

DIVERGENT NOZZLE

DE LAVAL NOZZLEA de Laval nozzle (or convergent-divergent nozzle, CD nozzle or con-di nozzle) is a tube that is pinched in the middle, making a carefully balanced, asymmetric hourglass shape. It is used to accelerate a hot, pressurized gas passing through it to a higher speed in the axial (thrust) direction, by converting the heat energy of the flow into kinetic energy. Because of this, the nozzle is widely used in some types of steam turbines and rocket engine nozzles. It also sees use in supersonic jet engines.The nozzle was developed by Swedish inventor Gustaf de Laval in 1888 for use on a steam turbine.This principle was first used in a rocket engine by Robert Goddard. Very nearly all modern rocket engines that employ hot gas combustion use de Laval nozzles.

WORKING PRINCIPLE OF A DE LAVAL NOZZLE

Imagine you are controlling the pressure in cylinder B, and measuring the resulting mass flow rate through the nozzle. You may expect that the lower you make the pressure in B the more mass flow you'll get through the nozzle. This is true, but only up to a point. If you lower the back pressure enough you come to a place where the flow rate suddenly stops increasing all together and it doesn't matter how much lower you make the back pressure (even if you make it a vacuum) you can't get any more mass flow out of the nozzle. We say that the nozzle has become 'choked'. You could delay this behavior by making the nozzle throat bigger (e.g. grey line) but eventually the same thing would happen. The nozzle will become choked even if you eliminated the throat altogether and just had a converging nozzle.

The reason for this behavior has to do with the way the flows behave at Mach 1, i.e. when the flow speed reaches the speed of sound. In a steady internal flow (like a nozzle) the Mach number can only reach 1 at a minimum in the cross-sectional area. When the nozzle isn't choked, the flow through it is entirely subsonic and, if you lower the back pressure a little, the flow goes faster and the flow rate increases. As you lower the back pressure further the flow speed at the throat eventually reaches the speed of sound (Mach 1). Any further lowering of the back pressure can't accelerate the flow through the nozzle any more, because that would entail moving the point where M=1 away from the throat where the area is a minimum, and so the flow gets stuck. The flow pattern downstream of the nozzle (in the diverging section and jet) can still change if you lower the back pressure further, but the mass flow rate is now fixed because the flow in the throat (and for that matter in the entire converging section) is now fixed too.

The flow accelerates out of the chamber through the converging section, reaching its maximum (subsonic) speed at the throat. The flow then decelerates through the diverging section and exhausts into the ambient as a subsonic jet. Lowering the back pressure in this state increases the flow speed everywhere in the nozzle.Lower it far enough and we eventually get to the situation shown in figure 3b. The flow pattern is exactly the same as in subsonic flow, except that the flow speed at the throat has just reached Mach 1. Flow through the nozzle is now choked since further reductions in the back pressure can't move the point of M=1 away from the throat. However, the flow pattern in the diverging section does change as you lower the back pressure further.As pb is lowered below that needed to just choke the flow a region of supersonic flow forms just downstream of the throat. Unlike a subsonic flow, the supersonic flow accelerates as the area gets bigger. This region of supersonic acceleration is terminated by a normal shock wave. The shock wave produces a near-instantaneous deceleration of the flow to subsonic speed. This subsonic flow then decelerates through the remainder of the diverging section and exhausts as a subsonic jet. In this regime if you lower or raise the back pressure you increase or decrease the length of supersonic flow in the diverging section before the shock wave.If you lower pb enough you can extend the supersonic region all the way down the nozzle until the shock is sitting at the nozzle exit (figure 3d). Because you have a very long region of acceleration (the entire nozzle length) in this case the flow speed just before the shock will be very large in this case. However, after the shock the flow in the jet will still be subsonic.Lowering the back pressure further causes the shock to bend out into the jet (figure 3e), and a complex pattern of shocks and reflections is set up in the jet which will now involve a mixture of subsonic and supersonic flow, or (if the back pressure is low enough) just supersonic flow. Because the shock is no longer perpendicular to the flow near the nozzle walls, it deflects it inward as it leaves the exit producing an initially contracting jet. We refer to this as overexpanded flow because in this case the pressure at the nozzle exit is lower than that in the ambient (the back pressure)- i.e. the flow has been expanded by the nozzle to much.

A further lowering of the back pressure changes and weakens the wave pattern in the jet. Eventually we will have lowered the back pressure enough so that it is now equal to the pressure at the nozzle exit. In this case, the waves in the jet disappear altogether (figure 3f), and the jet will be uniformly supersonic. This situation, since it is often desirable, is referred to as the 'design condition'.

Finally, if we lower the back pressure even further we will create a new imbalance between the exit and back pressures (exit pressure greater than back pressure), figure 3g. In this situation (called 'underexpanded') what we call expansion waves (that produce gradual turning and acceleration in the jet) form at the nozzle exit, initially turning the flow at the jet edges outward in a plume and setting up a different type of complex wave pattern.

CRITICAL PRESSURE RATIO

The maximum gas flow through a nozzle is determined by the critical pressure.• The critical pressure ratio is the pressure ratio which will accelerate the flow to a velocity equal to the local velocity of sound in the fluid.Critical flow nozzles are also called sonic chokes. By establishing a shock wave the sonic choke establish a fixed flow rate unaffected by the differential pressure, any fluctuations or changes in downstream pressure. A sonic choke may provide a simple way to regulate a gas flow. The ratio between the critical pressure and the initial pressure for a nozzle can expressed aspc / pi = ( 2 / (n + 1) )n / (n - 1) (1)wherepc = critical pressure (Pa)pi = inlet pressure (Pa)n = index of isentropic expansion or compression - or polytropic constant

steam transonic flows in Laval nozzles

In aeronautics, transonic refers to the condition of flight in which a range of velocities of airflow exist surrounding and flowing past an air vehicle or an airfoil that are concurrently below, at, and above the speed of sound in the range of Mach 0.8 to 1.0, i.e. 600–768 mph (965–1236 km/h) at sea level. In large output turbines, the state path usually crosses the saturation line in the penultimate stages. This means that at least last two stages of the low-pressure turbine operate in the two-phase region, producing much more than 10% of the total power output. The liquid phase in steam turbines is mainly created in the process of homogeneous and heterogeneous condensation. The part of the hetero-geneous condensation in liquid phase formation de-pends on steam purity. For the purposes of the prob-lems considered in this paper it was assumed that the steam was perfectly pure. The flow in the low-pressure steam turbine is com-plicated and still requires thorough experimental and numerical analysis to increase energy conversion ef-ficiency. Low-pressure turbine blades are key com-ponents in overall steam turbine design. A fully de-veloped 3-D stage flow analysis can provide an op-timum blade profile, capable of minimizing losses from shock waves caused by supersonic flow and also from condensation shocks.

Figure 1: Steam tunnel with auxiliary devices: 1) Control valve, 2) By-pass, 3) Stop gate valve, 4) Stop gate valve at by-pass, 5) Inlet nozzle, 6) Test section, 7) Outlet elbow, 8) Water injec-tor, 9) Pipe, 10) Safety valve, 11) Condenser, 12) Suction line, 13) Throttle valve, 14) Desuperheater, 15) Condensate tank, 16) Control system of condensate level, 17) Condensate pump, 18) Discharge line, 19) Stop valve, 20) Water injector pump, 21) Cooling water pump, 22) Condensate pump, 23) Pump

Construction of steam nozzleIf great pressure differences exist in front and at the back of inlet nozzles of steam turbines a secure attachment of the nozzles is sometimes rather difficult.The difficulties are eliminated by milling or otherwise machining the nozzles into a complete or undivided solid ring.An example is shown in the drawing affixed hereto.The single figure of the drawing shows a cross-section through one half of the nozzles.Referring to this figure it will be seen that the steam flows from the channel 6 in the casing 1 into the nozzles 7. These nozzles are machined into a solid ring 2 which is inserted into the turbine casing 1. The turbine may work with full or partial steam admission. A particularly good attachment of the ring 2 within the casing 1 is attained by shrinking the nozzle ring into the casing without making use of a special guide wheel body. The attachment of the ring 2 in the manner specified permits, however, of leaks as well relative displacements. According to a further development the nozzle ring is secured in position by a further locking ring. This ring is indicated in the drawing by the numeral 3, it is tightened up by cone head screws 8 and thereby forces a packing ring 5 against a shoulder on the ring 2 as well as on the easing 1. In order to make quite sure of a tight seal a ring 4; of soft metal is inserted between the adjacent surfaces of the casing 1 and the ring 2 by caulking. It is particularly applicable to super-pressure turbines.Various modifications and changes may be made.

In a steam turbine the combination of a casing, a nozzle carrier having nozzle grooves in its outer periphery and forming a complete solid ring located in the turbine casing, and having its outer periphery shrunk against the inner periphery of the turbine casing,which forms one of the nozzle sides, and a soft metal ring caulked between the inner ring surface and the casing so that the steam admitted to the nozzles can flow only substantially in the axial direction of the turbine. Materials used for construction of a nozzle are : Brass , Stainless Steel , Zinc Aluminum Alloy, Hot Pressed Boron CarbideThe construction of the nozzle was done with materials obtainable locally and the science of operation carried out in constructing the nozzle was; cleaning, marking out, cutting off, drilling, folding, centre punching, assembling, welding, filling, testing and painting.

The flow nozzle was constructed based on the following specifications and dimensions;Throat Diameter60mmThe diameter of the duct pipe 140mmThe length of the up stream pipe 200mmThe thickness of the nozzle3.8mmThe length of the down stream pipe 200mmThe height of the nozzle820mmThe length of the nozzle690mmThe size of the pressure valves ½ inchFurthermore, the selection of materials for the construction of this flow nozzle was based on the factors which includes; ductility, malleability, fabricability, mechanical strength and stability, availability, corrosion resistance and lastly cost factor.

Effects of friction on nozzle efficiency

For stream flowing through a nozzle, its final velocity for a given pressure drop is reduces to:

• Friction between nozzle surface and stream• Internal friction of stream itself.• Shock losses.Most of the frictional losses occur between the throat and exit in nozzle,

producing following effect.• Expansion is no more isentropic.• Enthalpy drop is reduced.• Final dryness fraction of steam increases.(kinetic energy- heat, due to friction

and gets absorbed.)• Specific volume of steam increases.(steam becomes more dry due to friction

reheating)

Parameters of steam nozzle Foundation Rotor or shaft Cylinder or Casing Blades Diaphragm Steam Chest Coupling Bearings Labyrinth seal Front pedestal TSI D-EHC(governor) MSV(main steam stop value) CV(control value)

IV(intercept value) CRV(combined reheat value) Turbine Turning Gear Turbine Bypass and Drains Lube oil system EHC oil system Gland steam systems Condenser Steam jet Ejector Vacuum Breaker

SUPER SATURATED FLOW When dry and saturated steam is caused to expand in a nozzle, the actual measured steam flow is found to be greater than the theoretical calculated flow. This is due to the time lag in the condensation of steam and the steam remains in dry state instead of wet. Such a steam is called supersaturated steam. This time lag is caused due to the fact that, the converging part of the nozzle is too short and the steam velocity is too high that the molecules of steam have insufficient time to form droplets.

EFFECTS OF SUPERSATURATED FLOW

Final dryness fraction increases.

Density of supersaturated steam is more than that for equilibrium conditions(As no condensation during supersaturated expansion => supersaturation temperature < saturation temperature corresponding to the pressure).

Thus , measured discharge (=>mass) is greater than that theoretically calculated.

MACH NUMBER Mach number is the ratio of flow velocity passed the boundary to the local speed of sound. It is a dimensionless quantity:- M=u/cWhere, M= Mach Number. u= Local flow velocity with respect to the boundaries. c= Speed of the sound in the medium.

If , M>1, the flow is supersonic M<1, the flow is subsonic M=1, the flow is sonic

Figure 4: Calculated Mach number distribution (top) and Schlieren pictures from experiment for D1 nozzle

APPLICATIONS OF STEAM NOZZLE

To rotate steam turbine.

Thermal power plant.

Steam nozzle are also used for cleaning purpose.

To produce a very fine jet spray.

THANK YOU

References/Bibliography-Wikipedia.org Patents.google.com NPTEL(IITKGP) Random JournalsContents,Animations & Slide design-Rohan Roy